Safety device for aeroplanes



M. J. R EINHARD SAFETY DEVICE FOR AEROPLANES Filed Nov. 23. 1928 6 Sheets-Sheet l M f/w/ M INVENTOR.

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SAFETY DEVICE FOR AEROPLANESI Filed Nov. 23. 1928 6 Sheets-Sheet 3 INVENTOR.

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244. AtRUNAu mo Aug. 12, 1930. M. J. REINHARD 1,772,962

7 SAFETY DEVICE FOR AEROPLANES Filed Nov. 23. 1928 6 Sheets-Sheet 4 INVENTOR.

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Patented Aug. 12, 1930 ATENT OFFICE MARTIN J". REINHARD, OF CHICAGO, ILLINOIS SAFETY DEVICE FOR AEROPLANES Application filed November 23, 1928. Serial No. 321,323.

The invention relates to aeroplanes and the like, and the object of the invention is to provide an aeroplane with means for preventing said plane from crashing to the ground in consequence of a so-called nose dive.

A further object of the invention is to provide an aeroplane in addition to the usual supporting or flying wings with an extra set of wings, which commonly act in the capacity of auxiliary wings, but are adapted to be manipulated by the aviator in such a manner,

that they will act as a brake in case the aeroplane equipped with said additional or auxiliialry wings should go into a so-called nose Another object of the invention is to provide an aeroplane with a set of auxiliary wings, which may be adjusted by the aviator in such a manner as to urge the forward portion of the plane upwardly.

Other objects of the invention not specifically mentioned may be easily ascertained and understood from the following descripdrawings.

tion in connection with the accompanying Said drawings illustrate a preferred embodiment of the invention, and it 'is to be understood, that the invention is not g to be restricted or limited to the exact construction and formation shown in the drawings and described in the specification, but that the invention is only to be limited by the scope of the claims appended hereto.

In the drawings:

Fig. 1 is a partial side elevation of the aeroplane according to the present invention, the propeller and the usual steering apparatus being omitted.

Fig. 2 is a sectional view taken on line 22 in Fig. 4.

Fig. 3 is a front elevation of the aeroplane.

Fig. 4 is a sectional view taken on line 4-4 in Fig. 1.

Fig. 5 is a sectional view taken on line 55 in Fig. 1.

Fig. 6 is a sectional view taken on line 6-6 in Fig. 5.

Fig. 7 is a detail View of a part of the means for adjusting the position of the auxiliary wings, and

Fig. 8 is a top view of the forward portion of the aeroplane, a part of the auxiliary wings being broken out in order to facilitate the illustration of the means for adjusting and guiding said wings.

The body 10 of the aeroplane may be of any suitable and desirable material and construction. It does not constitute any part of the invention proper and is therefore not shown or described in detail. On the tail end of the aeroplane the usual steering apparatus is to be provided, but this is also omitted in the drawings and is only mentioned here to facilitate the understanding.

On the fore-part of the body, preferably somewhat below the horizontal center plane of said body, the main flying or supporting wings 11 are fastened to the body in any convenient and suitable manner, and said main wings may be of any known and desired construction. As clearly shown in the drawings the main wings are arranged on the forward part of the aeroplane, but still somewhat to the rear of the foremost part thereof. Preferably said wings are arranged so, that the forward part thereof is located right above the forward wheels 12 of the landing ear.

Above the main wings and forwardly thereof a set of auxiliary wings 13 is provided forming the main subject of the present invention. These wings are preferably constructed as one unit. A pair of strong vertical rocker plates 14 extend downwardly from said wing unit. Said rocker plates are arranged adjacent the body of the aeroplane, one at each side thereof. Each of said rocker plates is provided with a curved slot 15 and a trunnion 16 or the like, fastened to the body of the aeroplane extends through each of said slots. On the lower face of the auxiliary wing unit and arranged between the rocker plates a plurality of female guide members 17 are fastened and extend downwardly thereof. A corresponding number of male guide members 18' is fastened to the body of the aeroplane. All the guide members are curved on the same center as the curved slots 15 in the rocker plates 14, i. e. the curvature of said members and said slots is such, that the auxiliary wing unit may be moved so,

that the wing surface may form angles of different degrees with the horizontal, while the trunnions 16 and the guide members 18 guide the unit during its adjustment, said trunnions freely sliding in the slots 15 and the guide members 18 moving in the corresponding members 17.

The mechanism for adjusting the wing unit in any desired angle and holding it in posi tion after being adjusted is preferably constructed as follows:

Adjacent the pilot seat 19 a hand wheel 20 is rotatably mounted, and a bevel gear 21 is rigidly connected therewith. Preferably the axis of these two members extends horizontally. A shaft 22 is journalled vertically in the body of the aeroplane and a bevel gear 23, which is rigidly mounted on the upper end of said shaft, meshes with the first bevel gear 21. On the lower end of the shaft 22 a third bevel gear 24 is rigidly mounted. Two horizontally extending shafts 25 and 26 are journalled in hangers 27, 28, 29, and 30 fastened to the body of the aeroplane, and extend toward the sides thereof. On the inner end of each of the horizontal shafts a bevel gear 31 and 32 respectively is rigidly mounted. Both of these bevel gears mesh with the bevel gear 24 on the lower end of the vertical shaft 22. On each of the outer ends of the horizontal shafts 25 and 26 another bevel gear 33 and 34 respectively is rigidly mounted. Each of these bevel gears meshes with another bevel gear 35 and 36 respectively, and these bevel gears are fast each on a vertically j ournalled shaft 37 and 38 respectively. On the lower end of each of these shafts a bevel gear 39 is rigidly mounted meshing with another bevel gear 40 fast on a horizontal shaft 41, which is journalled in a bearing 42 fastened to the inner face of each side wall of the aeroplane body. On the other end of each of said horizontal shafts a spur gear 43 and 44 respectively is rigidly mounted.

On the outside face of each side Wall of the aeroplane a housing 45 is fastened. Each housing consists of a forward part 46 and a rear part 47.

A spur gear 48 has on each of its sides two concentric bosses 49 and 50. The abutting ends of the housing parts are shaped in such a manner, that two internal ring shoulders 51 and 52 will be formed on each part. These shoulders cooperate with the concentric bosses 49 and 50 of the spur gear 48 to journal the latter.

In each of the side walls of the aeroplane adjacent each of the first mentioned spur gears 43 and 44 on the two horizontal shafts 41 a slotlike opening 53 is provided, so that the corresponding pairs of spur gears can extend through said wall and mesh with each other.

Each of the outside spur gears 48 has a central, axially extending bore, and this bore is provided with a female thread. It is to be noted, that the thread in one of said spur gears has to be right hand and the other left hand. A threaded spindle 54 and 55 respectively is arranged in each of the housings and the thread thereof meshes with the thread of the corresponding spur gear. The spindle extends through the corresponding gear and to the forward end of each spindle a connecting rod 56 is pivotally jointed.

Each rocker plate 14 has downwardly and rearwardly extending ear 57. The forward end of the connecting rod 56 is forked, and the ear is engaged by this fork. A stud 58 or the like extends through registering holes provided in said members and pivotally connects said parts with each other.

The device operates as follows:

When the aviator takes off, he manipulates the hand Wheel 20 so that the two spindles will be in their rearmost position. Then the auxiliary Wing unit will stand parallel to the main wings, so that the aeroplane may then be considered to be a double decker.

Should the aeroplane during a flight accidentally get into a nose dive, the aviator will operate the handle to set the auxiliary wing unit at an angle to the main wings. The air pressure will engage the undersurface of the said auxiliary wing and will urge the fore part of the aeroplane upwardly, thereby forcing it out of the nose dive and if not actually entirely preventing the consequent accident, at least greatly reducing the force of the descent of the aeroplane. The auxiliary wing unit may therefore be looked upon as an emergency brake.

Having described my invention and how the same is to be performed I claim as new and desire to secure by Letters Patent:

1. In an aeroplane a body, a set of wings, a pair of rocker plates on said wings, each plate being provided with a curved slot therein, a pair of trunnions on said body, one of said trunnions slidably extending through each of said slots, and means for angularly adljusting said wings relative to the horizonta 2. In an aeroplane a body, a set of wings adjacent the forward end thereof, a pair of rocker plates on said wings and extending downwardly therefrom, each plate being provided with a curved slot therein, a pair of trunnions on said body, one arranged on each side wall of the body and extending laterally thereof and through the slot in the adjacent rocker plate, a connecting rod pivotally fastened to each rocker plate means for longitudinally moving said connecting rod, and means adjacent the pilot seat for controlling said first mentioned means.

3. In an aeroplane a body, a pilot seat in said body, a set of wings extending crosswise of and over the front part of the body, a

244. AtHUNAu we pair of rocker plates on said wings and extending downwardly thereof, one adjacent each side wall of said body, a trunnion on each side wall, each rocker plate having a curved slot therein, one of said trunnions slidably extending through one of said slots, a plurality of guide members on said body, a corresponding number of guide members on said wings, means for angularly adjusting said win s relative to the horizontal, and means ad acent the pilot seat for controlling said first mentioned means.

4. In an aeroplane a body, a set of wings extending crosswise of and over said body, a pair of rocker plates on said Wings and extending downwardly thereof, a plurality of guide members on said body, a corresponding number of guide members on said wings, a pair of connecting rods, one of said rods being pivotally fastened to each of said rocker plates, a pair of sliding members, one of said members pivotally fastened to each of said connecting rods, means for guiding said sliding members, and means for axially moving said sliding members in either direction.

In witness whereof I aflix my signature.

MARTIN J. REINHARD. 

